US3749047A - Combined gas turbine - Google Patents

Combined gas turbine Download PDF

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Publication number
US3749047A
US3749047A US00165130A US3749047DA US3749047A US 3749047 A US3749047 A US 3749047A US 00165130 A US00165130 A US 00165130A US 3749047D A US3749047D A US 3749047DA US 3749047 A US3749047 A US 3749047A
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United States
Prior art keywords
turbine
combustor
deck
ship
compressor
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US00165130A
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English (en)
Inventor
S Tamaru
K Teshima
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsui Engineering and Shipbuilding Co Ltd
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Mitsui Engineering and Shipbuilding Co Ltd
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Publication date
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/36—Open cycles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H21/00—Use of propulsion power plant or units on vessels
    • B63H21/12—Use of propulsion power plant or units on vessels the vessels being motor-driven
    • B63H21/16—Use of propulsion power plant or units on vessels the vessels being motor-driven relating to gas turbines
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • ABSTRACT A gas turbine arrangement for ships in which a low temperature turbine using low grade fuel is mounted above the deck and is directly coupled to a compressor for a second turbine mounted in the engine room which operates at high temperature and with high quality fuel. The entire output of the second turbine drives the ship propeller, preferably through reduction gearing.
  • the compressed air from the above-deck turbine may be heated by the exhaust gases from the below-deck turbine.
  • the above deck turbine may be a two-stage arrangement having an intercooler between the two stages of compression. Additionally a bleeder system and heat exchanger may be incorporated in the output of the first compressor.
  • M B2 is that suction air volume of the 1 COMBINED GAS TURBINE
  • the present invention relates bine effectively used for ship.
  • the gas turbine is light in weight and small in size but large in output, and thereby widely used for aircraft.
  • application of gas turbine to ship is extremely limited and only found specifically in naval craft. The reason for this is that the use of low grade fuel is difficult because of increase of fuelexpense. Further reason gas turbine per output of exhaust gas generto a combined gas turis large, thereby a large amount ated and a large sectional area of exhaust ducts required in spite of the fact that the gas turbine engine itself is small in. size. These factors are of course. disadvantageous to apply the gas turbine to ships.
  • the present invention has for its object to remove the above mentioned disadvantages, and is characterized in that two or more gas turbines are combined to form a composite cycle, so that. amount of suction air introduced in the output turbine isdecreased, and thereby decreasing cross-sectional area of the suction and the exhaust ducts thereof.
  • the combined gas turbine in accordance with the present invention are. such composed that an air compressor is driven by. means of an independent gas turbine which consumes chiefly low grade fuel such as Bunker C heavy oil or Heavy Marine Fuel Oil and high pressure air discharged from the compressor is introduced into combustor of output turbine and then the produced hightemperature and high pressure gas is introducedintothe output turbine to obtain output.
  • an independent gas turbine which consumes chiefly low grade fuel such as Bunker C heavy oil or Heavy Marine Fuel Oil and high pressure air discharged from the compressor is introduced into combustor of output turbine and then the produced hightemperature and high pressure gas is introducedintothe output turbine to obtain output.
  • FIGS. 1a and lb are schematic diagrams showing conventional gas turbines
  • FIG. 2 is a schematic diagram showing the present invention
  • FIG. 3 is a schematic diagram showing a case in which the present invention is applied to ships.
  • FIGS. 4 through.8 are schematic diagrams showing other embodiments of the present invention applied to ships respectively.
  • the combined gas turbine comprises ,a compressor side C and an output side D.
  • the compressor side comprises a compressor C combustor 8,, output turbine T, and compressor C, connected to the output shaft of the turbine T
  • the high pressure air. discharged from the compressor C is introduced in the combustor B, of the output side turbine'to drive the turbine T
  • W the requiredpower for compressor
  • .flow rate of air introduced into the combustor B, by means of the compressor C is about two point three times as much as that of the combustor 8,.
  • fuel consumption ratio of the combustor B is about percent of whole fuel consumption of the conbined turbine.
  • the present invention can provide an economical combined turbine by using a low grade fuel in the combustor B of large fuel consumption ratio, even if the fuel consumption rate per output is increased owing to low gas temperature below 750C. While, high quality fuel such as light oil is used in the combustor 8,, high power output is obtained by raising the gas temperature.
  • the above rough calculation is based on an assumption that the combustors B and B are equal in temperature. However, the temperature of the combustor B is elevated higher than that of the combustor B Accordingly, the ratio of the required air volume is slightly different from the above value.
  • FIG. 3 of the present invention.
  • the compressor side C shown in FIG. 2 is located above the deck and the output side D is arranged in the engine room and connected through the reduction gear R6 to the propeller.
  • GT (I) shown in the drawing represents the turbine of the compressor side in block.
  • the duct system in the hull is enough to provide a duct for air to be supplied to the combustor B: only and the amount of air is only about one-thirds of the total required air as mentioned above.
  • the air flowing into the combustor B has been compressed by the compressor C below one-fifth or less of the initial volume, consequently, the cross-sectional area of the duct required for necessary output is reduced to one-tenth or less as compared with conventional systems.
  • the efficiency of the turbine may be improved by employing various known means such as preheating by e'xaust gas, two-stage compression, inter cooling, bleeder system, etc. as shown in FIGS. 4 through 8.
  • GT (II), HE and IC shown in the drawings indicate a turbine, heat exchanger and inter coller respectively.
  • the economy of fuel cost is improved as a whole by using low grade fuel in the large ratio to whole fuel consumption, as well as the cross-sectional area of the air suction and exhaust ducts can be remarkably reduced.
  • the gas turbine consuming low grade fuel is located above the deck, maintenance of the gas turbine is easy.
  • a combined gas turbine drive for ships according to claim 1 including means to couple the entire output of said second turbine to the ship propeller.
  • a drive for ships including a heat exchanger to receive exhaust gases from the second turbine, and means to direct compressed air from said compressor through said heat exchanger prior to passing into said combustor.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • Ocean & Marine Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
US00165130A 1970-07-28 1971-07-22 Combined gas turbine Expired - Lifetime US3749047A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP45066000A JPS4910762B1 (enrdf_load_stackoverflow) 1970-07-28 1970-07-28

Publications (1)

Publication Number Publication Date
US3749047A true US3749047A (en) 1973-07-31

Family

ID=13303228

Family Applications (1)

Application Number Title Priority Date Filing Date
US00165130A Expired - Lifetime US3749047A (en) 1970-07-28 1971-07-22 Combined gas turbine

Country Status (6)

Country Link
US (1) US3749047A (enrdf_load_stackoverflow)
JP (1) JPS4910762B1 (enrdf_load_stackoverflow)
DE (1) DE2137531A1 (enrdf_load_stackoverflow)
FR (1) FR2099644B1 (enrdf_load_stackoverflow)
GB (1) GB1304318A (enrdf_load_stackoverflow)
NL (1) NL7110314A (enrdf_load_stackoverflow)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4988489A (en) * 1989-01-25 1991-01-29 Todd Lanny E Recovery of phosphorus values from waste phosphoric acid liquors
US5433069A (en) * 1991-12-02 1995-07-18 Fluor Corporation Process and economic use of excess compressed air when firing low BTU gas in a combustion gas turbine
US20180080378A1 (en) * 2016-09-16 2018-03-22 Pratt & Whitney Canada Corp. Multi-engine aircraft power plant with heat recuperation

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2241202A1 (de) * 1972-08-22 1974-03-07 Motoren Turbinen Union Gasturbinenanlage mit waermetauscher
US5181376A (en) * 1990-08-10 1993-01-26 Fluor Corporation Process and system for producing power

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR994281A (fr) * 1941-08-08 1951-11-14 Rateau Soc Appareil moteur à turbines à gaz pour entraînement direct de véhicules
FR977736A (fr) * 1942-10-26 1951-04-04 Rateau Soc Perfectionnements apportés aux moteurs thermiques à turbines à gaz pour le fonctionnement dans les deux sens de marche
GB622053A (en) * 1946-04-15 1949-04-26 Oerlikon Maschf Improvements in or relating to gas turbine plant
FR1002468A (fr) * 1946-10-07 1952-03-06 Rateau Soc Moteurs à turbines à gaz pouvant fonctionner avec ou sans air atmosphérique notamment pour la propulsion des navires de guerre
DE941240C (de) * 1953-10-17 1956-04-05 Weser Ag Gasturbinenanlage mit Vor- und Rueckwaertsturbine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4988489A (en) * 1989-01-25 1991-01-29 Todd Lanny E Recovery of phosphorus values from waste phosphoric acid liquors
US5433069A (en) * 1991-12-02 1995-07-18 Fluor Corporation Process and economic use of excess compressed air when firing low BTU gas in a combustion gas turbine
US20180080378A1 (en) * 2016-09-16 2018-03-22 Pratt & Whitney Canada Corp. Multi-engine aircraft power plant with heat recuperation
US10760484B2 (en) * 2016-09-16 2020-09-01 Pratt & Whitney Canada Corp. Multi-engine aircraft power plant with heat recuperation

Also Published As

Publication number Publication date
FR2099644A1 (enrdf_load_stackoverflow) 1972-03-17
NL7110314A (enrdf_load_stackoverflow) 1972-02-01
FR2099644B1 (enrdf_load_stackoverflow) 1975-02-07
DE2137531A1 (de) 1972-02-03
JPS4910762B1 (enrdf_load_stackoverflow) 1974-03-13
GB1304318A (enrdf_load_stackoverflow) 1973-01-24

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